Ignition Testing of U.S. Army Rocket Launch Tubes with Comparative Heat Transfer Analysis

dc.contributor.advisorMilke, James Aen_US
dc.contributor.authorOzog, Nicholas Een_US
dc.contributor.departmentFire Protection Engineeringen_US
dc.contributor.publisherDigital Repository at the University of Marylanden_US
dc.contributor.publisherUniversity of Maryland (College Park, Md.)en_US
dc.date.accessioned2007-09-28T15:02:20Z
dc.date.available2007-09-28T15:02:20Z
dc.date.issued2007-08-07en_US
dc.description.abstractThe objective of this research was to determine the time to ignition of U.S. Army fiberglass epoxy rocket tubes in various conditions. Experiments were conducted using an oxygen calorimeter and a propane burner for determining the ignition time. The Biot number and heat transfer coefficient was determined. A lumped capacitance method was used to calculate the energy input. The energy input from the rocket plume into the tube was calculated using a semi-infinite solid with surface convection. The two energy calculations were compared indicating that approximately 1.4 rockets must be fired in rapid succession to lead to ignition conditions. Tube condition was found to have no affect on ignition time.en_US
dc.format.extent5781696 bytes
dc.format.mimetypeapplication/pdf
dc.identifier.urihttp://hdl.handle.net/1903/7369
dc.language.isoen_US
dc.subject.pqcontrolledEngineering, Generalen_US
dc.subject.pquncontrolledIgnition of Soliden_US
dc.subject.pquncontrolledSemi-Infinite Soliden_US
dc.subject.pquncontrolledBiot Numberen_US
dc.subject.pquncontrolledHeat Transfer Coefficienten_US
dc.subject.pquncontrolledOxygen Calorimeteren_US
dc.subject.pquncontrolledPropane Burneren_US
dc.titleIgnition Testing of U.S. Army Rocket Launch Tubes with Comparative Heat Transfer Analysisen_US
dc.typeThesisen_US

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